Preparation and high temperature resistance property of TPS material with integrated thermal insulation

Abstract

In order to meet the needs of large area thermal protection(≥1500 ℃)for high-speed aircraft, the high temperature resistant alumina fiber reinforced aerogel composite was used as the thermal insulation layer, and the carbon fiber fabric was used as the panel layer preform. Through the normal needle puncture process and the precursor impregnation pyrolysis process, the integrated TPS material for thermal protection was prepared, and the high temperature resistance performance tests were carried out to provide theoretical and technical support for the engineering application of materials. The results show that the integrated TPS material with good integrity and no obvious defects can be prepared by needle puncture suture technology and PIP process, and the density is only 0.6 g/cm3. When C/SiC composites are used in high-temperature oxidation environment, the oxidizing atmosphere diffuses into the material through defects such as pores and cracks, and oxidizes with carbon fibers, resulting in the degradation of composite properties. The material has excellent high temperature resistance, with mass ablation rate of 0.051 g/s and linear ablation rate of 0.077 mm/s; There is no obvious gap structure, and there is no obvious shrinkage on the whole, showing good high temperature resistance.

Keywords

• thermal insulation
• precursor infiltration pyrolysis
• integrated material
• engineering application
• high temperature resistance